Axial flow jet motor with rotating combustion products generator and turbine



2 SHEETSSHEET l flan/1Z0! PRODUCTS GENERATOR AND TURBINE D. W. SEIFERTAXIAL FLOW JET MOTOR WITH ROTATING COMBUSTION 7 34 5w. 9 0 ,2 0. h C up.QW n N.

March 10, 1953 D. w. SEIFERT 2,630,675

AXIAL FLOW JET MOTOR WITH ROTATING COMBUSTION PRODUCTS GENERATOR ANDTURBINE Filed Jan. 20. 1947 2 smzms-sm-zsw 2 g x .96 122 48 52 k w w% I/fi8 124 7 Q0 NVENTORI Z 24 DonaZdZJSezlfer Patented Mar. 10,1953

UNITED STATES PATENT OFFICE AXIAL FLOW JET MOTOR WITH ROTATINGCOMBUSTION PRODUCTS GENERATOR AND TURBINE Donald W. Seifert, Winona,Minn. Application January 20, 1947, Serial No. 722,987 r 17 Claims. (01.(so-39.35) 1 This invention relates to jet motors.

The jet motor of the present invention i'sof the type which is propelledby expulsion of gases rearwardly out of the motor, and which picks upair for combustion when traveling. This is distinguished from rockets inwhich the air for combustion is contained in the fuel provided in thedevice. By way of general explanation, the present invention applies tothat type of fuel burning device in which the device is propelledforward by rearward expulsion of gases of combustion; the gases ofcombustion in the same propelling process rotate a driving element whichin turn operates a compressor. The compressor then picks up air in thetravel of the device, compresses it, and delivers it to the drivingelement where it supports combustion of the fuel.

An important advantage resides in this feature; in previous jetpropelled devices, the combustion chamber was stationary, and the gasesof combustion were then driven through a turbine which operated acompressor. In the device of the present invention, a plurality ofcombustion chambers are arranged in a rotating driving means, where thecombustion takes place, so that the actual process of combustionproduces a direct and immediate rotating force on the driving means.

The combustion driving means above referred to may also be referred toas an athodyd or athodyd stage. Athodyd" is a word recently coined fromaero-thermo-dynamic-duct, and applies particularly to jet motors. Thisdriving element may be referred to herein both as an athodyd drivingmeans and a combustion driving means.

A portion of the power generated by the expulsion of gases out of themotor is utilized in driving the compressor but the air compressed bythe compressor accomplishes more rapid combustion, resulting in higherspeeds of the device.

Accordingly, the efficiency of such a device is increased as the speedof the motor is increased. This is a peculiarity of jet motors, andbecause of that condition, when the efficiency drops to a certain point,operation of the device ceases. As a correlative of this phenomenon, thedevice must be given an impulse by some auxiliary force to attaininitial speed for the jet propulsion feature to become effective.

The present invention utilizes an elongated cylindrical casing; a shaftis rotatably mounted centrally of the casing, and the compressor andathodyd stage mentioned above are rotatably 2 mounted on the shaft. Thecasing is open at both ends taking in air at one, end and expelling; itat the other end. 1; Fuel is supplied to the athodyd driving means. andan ignition, device is provided for initial starting of the device.After the motor operates for a short time, the athodyd driving meansbecomes heated and the heat therefrom ignites the fuel; thereafter theignition system is no longer required.

Another phenomenon peculiar to jet motors is that while both ends areopen, the expulsion of gases is effected only in one direction, such expulsion being in the same direction as the influx of air which isbrought in by the travel of the machine. The incoming air is compressedinside the motor and drives the gases of combustion out the oppositeend.

An object of the present invention is the provision of a jet motor inwhich air compressed by the compressor-is deflected in a direction to beforced into an athodyd driving means. i

Another objectis the formation of the athodyd combustion driving meansfor eiilciently scooping up the compressed air deflected into it.

Afurther object of the invention is that the injection of fuel into thecombustion driving means is assisted by the rotation of the drivingmeans.

Still another object is the provision of a shape of combustion spaces inthe driving means to render thepropulsion effect of the device and theturning force on the driving means, by the gases of combustion, moreefllcient.

With these and other objects inview, my invention consists in theconstruction, arrangement and combination of the various parts of mydevice whereby the objects contemplated are attained, as hereinaftermore fully set forth, pointed out in my 'claims and illustrated in theaccompanying drawings, wherein:

Figure 1 is a longitudinal sectional view of a portion of the jet motorof my invention;

Figure 2 is a developed partial view of the compressor and combustiondriving means of the jet motor, as viewed from immediately inside thecasing of the motor;

Figure 3 is a sectional view taken on line 3-3 of Figure 1;

Figure 4 is a longitudinal sectional view of a modified form of jetmotor; and

Figure 5 is a longitudinal sectional view of a third type of jet motor.a l

The device of Figures 1 to 3 Referring now in detail to the drawings,the jet motor shown in Figures 1 and 2 includes a cylindrical casing I2having a leading open end I4, and a trailing open end IS. The trailingend It is developed along airflow lines and terminates at a reducedcylindrical outlet I8; If desiredthe shape of the casing I2may betaperedv along air flow lines to produce more efiicient air flow, and

the working parts designed to conform to the;

shape of the casing.

Mounted centrally, axially ofthecasing I2 is a rotatable shaft 2|]supported atone end bya bearing support indicated generally at 22 and atthe other end by another support indicated generally at 24. The bearingsupport 22 consists of a solid central portion 26 and" outwardly of theportion 26 are a plurality of blades 28 having their outer ends fixedlysecuredin the casing I2. The shape and. disposition. of these. blades28, will be referredto later. Acentral' opening, is formed in thecentral portion 26 of the, bearing support 22, for supporting ananti-friction bearing 30 in whichv the respective end of the shaft 26 issupported. The bearingv 3!] maybe secured in place by a plate-32Vsecured to thebearing support 22.

Securedtothe leading end of the shaft 26 is a gear. 34. meshingwith'.another. gear 35 which is mounted on a trunnion 38 which in turn ismountedon the bearing support 22.

Thebearing support 24' includes a central hub 40.,of enlarged dimensionsand 'a central portion 42.. outwardly of the'central, portion 42 are aplurality of bladesor fins '44, shown in Figure 2, secured. in theirextremities to the casing I2.

I A turbocompressor is indicated generally at 46,- and" includes arotary element 48. The rotary elementincludes a pair of end plates ordiscs 59 secured to the shaftZIJin aconventional manner, and acylindrical member 52 fitted on the end plates 50." Securedtothe-outersurface of the cylindricaljmember 52 area plurality of sets of blades54'spaced axially along the member'52. The blades 54 are'placedaroundthe member 52 as will be understood-by'those: familiar with turbines.

Spaced between-adjacentsets of blades 54 are setsxofci'ixedstationarybuckets 56;. The buckets 56 are fixed to the inner surface of thecasing. l2 and-extend between the: blades .54- down to a point adjacentthe memberv 52.

. Theathodyd driving means is indicated gen erally'at58. The driving.element includes a hub 54 in the form of. a hollow drum and is made upof an innertubular member 65 and an outer tubular member 68 secured"together and sealed by sideplates-IU.

' Secured to theouter surfaceof the outer tubular member are a pluralityofblocks or blades I2. Theblades I2 are secured to the, tubular member68, by means of bolts I4 extending through openings in the tubularmember 68 and threaded into tapped holes in the blades I2. Several suchboltsfi lmaybe employed in each blade .12; A coppercompression ring I6surrounds each bolt I4 and fits in an annular seat in the tubularmember-68, and-isadapted to be wedged therein by the bolt head. Thiscopper ring forms a seal as well ast ameans for retaining the bolt I4 intightened condition. A tube 'IBextends-through the outer tubular member68 adjacent each blade I2; and connectswith an opening or passage-8Bleading, from the tube I8 radially outwardly through the respectiveblade12. The passages 80 terminate in jets 82 which extend and open 4 in adirection opposite of and tangential to the direction of rotation of theblades I2.

Between adjacent blades 12 are spaces 84 in which combustion of the fueltakes place. The shape of these spaces 84 is determined by the shape ofthe blades I2, and each space 84 in cludes a restriction 86 at the rightend, or inlet, and a restriction=88 at theleft end, or outlet. Beyondthe-'restrictionsllfi and 88 are diverging spaces 90 and 92.

The blades I2 are positioned on the drum 64 at an angle .thereto thatis, each blade is turned on its own radial axis and positioned at anangle to the aXis of the driving means 58, and shaft 20.

The driving means 58 is supported on the shaft 20 by-means of aplanetary gearing indicated generallyat 93, and which includes a ringgear 94 on the periphery of which the tubular member 66"issplined asindicated at 96. Certain of the splines 96 may be enlarged for thepassage of air therethrough. The Weborcentral portionof thering gearstructure is supported or1 asleeve 98' secured to and v rotatable onthezshaft' 20; A'

plurality of' planetary gears I05 mesh with; the} ring gear 94 and aresupported on trunnions I02 secured in the bearing support 24. The outer;

ends of-the trunnions I02 are fitted with a ring; IM to preventcantilever action, and consequent binding, on thetrunnion supports I02.The planetary gears. IDEI mesh with a: sun gear IIIIi mounted directlyon the shaft 20'.

A shield I68, having atcentral opening for surrounding the trunnionsupports I02, has an axial flange for locating. it on the ring. gear94.. The shield I08 may be secured to the ring gear 94 in such' a manneras to slide axially thereon and is biased toward the-bearing; support 24by means of compression springsIIB. The shield Hi8. serves as a greaseretainer, for the planetary gearing 93;.

The sleeve98 is secured onto the shaft 20 by means of a block II2,threaded in the rear end of the sleeve; the block II2 seatsvagainst theinterior shoulder in the. sleeve 98 and-against anti-frictionbearing II4 whichfits in an annular recess H5. in the rear end of the. shaft 20.Another anti-friction bearing IIS is provided between the sleeve 98 andthe. shaft 20 ahead of the bearing H4. Seals IIll are provided betweenthe sleeve. 98. and shaft 28 at spaced points therein for. a purpose tobe shown later. and are heldIin place therein bythe usualretainingrings. Fuel is supplied by. means of an exterior fuel line I20which leads to a passage I22 in. one of the fins 44 and through thecentral portion d2; of the bearing support 24. The passage I22 thenleads through the enlarged hub. 40 of the interior thereof and into apassage I24 in the shaft 20. The interior of the hub- 40 may be sealedby seals I26. An additonalantifriction bearing I 28 isprovided betweenthe shaft Zil-and the hub 40. The passage in the. shaft 20 1eadsrearwardly and. opens into the sleeve 98 between; the seals II 8. Theseals II! therefore act as. retainers for the fuel passing throughpassage I24. From this space a. tube I30 leads to the interior of thehollow drum 64 from'there through the passages I8 and to the jets 82.

In the fin 44- in which the fuel passage I 22 is formed; an auxiliaryoutlet I32 opens rearwardly adjacent the blades I2 in the athodyddriving means 58; A solenoid operated closure I 34 extends into theoutlet. [-32 for controlling the same. An ignition glow plug I 35 ispositioned adjacent: the out1etil32,.and in surroundine:1:ela-

The ignition glow plug means I36 is Venturishaped, so that when the fuelfrom the outlet I32 passes therethrough it will be more readily ignited.

An inner shield I48 encloses the forward end of the central area of theinterior of the motor leaving an annular passage I42 therearound. Thispassag I42 corresponds with the radial area occupied by the blades 54and buckets 56 of the turbocompressor, and the blades I2 of the drivingmeans 58. A similar shield I44 is provided at the rear and may be fixedto the rear end of the sleeve 98' by means of a plate I 48. The shieldI44 is similar in outline to the rear end I6 of the casing and formstherewith an outlet passage I48.

Operation of the device of Figs. 1 to 3 A motor generator may be coupledwith the gear 38 for starting purposes. To start the jet motor thestarting motor is started which rotates the compressor and athodyddriving means up to a certain speed. The device, when operated up to thespeed possible by the starting motor, produces compressed air by thecompressor, which is forced rearwardly to the athodyd driving means 58,and ultimately out of the motor rearwardly.

Fuel emerges out of the outlet I32, and out of the jets 82; theauxiliary ignition means I38 is connected, which ignites the fuelleaving the outlet I32, which then ignites the fuel leaving the jets 82in the athodyd spaces between the blades I2.

Both the propelling effect of the motor, and the rotary force on theathodyd driving means 58 is caused by the combustion of gases in thespaces 84 after compressed air is built up therein. The gases ofcombustion are forced rearwardly by the compressed air, and the reactionof the expulsion of gases of combustion forces the device forward; atthe same time the reaction of the expulsion of the gases of combustionout of the spaces 84 produces a turning effect on the driving means 58due to the angular disposi-- tion of the latter with respect to the axisof the shaft 28.

The combustion thus produced rotates the athodyd driving means 58faster, which in turn rotates the compressor faster, and builds upgreater pressure of air.

and burns therein. The combustion heats the blades 12 to such a degreethat after initial starting by auxiliary means, the heat from the bladesI2 causes the ignition of the fuel. After:

the driving means 58 is thus rotated for a time and becomes heated, theignition means I36 can be cut out and the solenoid operated closure I34closed. At the same time the starting motor may be automatically cutout.

By the time the fuel emerges from the jets 82 it is fully vaporized. Thecentrifugal force of the athodyd driving means throws the fuel in thedrum 84 against the tubular member 88, outwardly beyond the inner endsof tubes I8, and heat conducted from the blades 12 vaporizes it. Suchvaporized fuel then passes through the passages I8 and 80, and out thejets 82.

, However, when the device is being started, fuel in liquid form mayemerge from the jets. Fuel The fuel emerging out of the jets 82 entersinto the spaces 84 is pumped into the drum 84 until it is deep 82 addsto the force of combustion in rotating the driving means similar to theaction of a lawn sprinkler.

The turbocompressor 46 is similar in construc-" tion to a steam turbine,but of course in the present instance the operation is reversed foraccomplishing the results of a compressor. Fins 28, buckets 58 and fins44 operate to direct air in certain given directions through thecompres- The blades 54 are arranged at different angles successivelythrough the motor from the leading end to the trailing end as indicatedin Figure 2. Finally the fins 44 are directed in a direction fordeflecting the compressed air in a particular direction into thecombustion driving element 58. Each set of buckets 5B deflects airbetween successive sets of blades 54 so that the succeeding set ofblades 54 produces a maximum compression effect. The fins 44 arepositioned at nearly the same angle relative to the axis of the shaft 20as the angle of the blades I2 of the driving means 58. The air isthereby deflected as nearly directly into the spaces 84 as is possible.The diverging spaces at the leading ends of the spaces 84 are adapted toscoop up the entering air more readily, and the trailing divergingspaces 82 accomodates the exhaust gases more readily.

The expulsion of gases of combustionreacts against such compressed airand the blades I2 to rotate the blades in the direction indicated by thearrow in Figure 2. The planetary gearing 93 through which the drivingmeans 58 is con nected with the shaft 28 reverses the direction ofrotation between the driving mean and the compressor.

The expulsion of gases of combustion at the rear opening I48 drives themotor ahead. and in such forward travel air is scooped up in the leadingopen end I4 where it is compressed by the compressor. The greater thecompressed air built up by the compressor, the greater i the expulsionof gases out of the rear end and vice versa, thus resulting in anarrangement whereby the faster the motor travels the more efiicientitbecomes. 8

One of the fins 44 may be enlarged to accommodate the fuel line I22, asshown in Figure 3, and certain others of the fins may be formedsimilarly for symmetry. Figure 2 shows the fins 44 diagrammatically, toshow their angular disposition, and to illustrate their function indirecting air into the spaces 84 of the driving means 58.

The gearing 34-46 may be utilized for driving auxiliary equipment suchas lighting on a ship in which the device is used.

As an alternative, jets may be provided in only The device of Figure 4The essential difference between the device of Figure 4 and that ofFigure 1 is that the turbocompressor is made up of counter rotatingelements. The differences in detail between the two figures willbeqpointd out hereinafter, and.

the similarities; will not be dwelt. upon.

The; turbocompresson in .Figure 4 is indicated generally at I50 andcomprises a central rotary element I52 secured on the shaft I54. Therotary element, I52 i -provided with a plurality of sets of curvedblades, I56 inc1ined successively toward the axialfrom the inlet M tothe rear, similarly to those of, Figure 1. Although the blades I56 areinclined similarly to the blades 54 of Figure 1, they are also curvedsimilarly to the buckets 5B of Figure l, to producemore efficient actionof the compressor.

An-outer rotary elementindicated generally at I5 1 su rrounds thecentral rotary element and includes adrum or cylindrical member I58having. a plurality of sets of inwardly extendingbucketsQIIiI]positioned between adjacent sets of blades I56. The outer rotary elementi5l' is freely-rotatable on theshaft I54. Fins ISZ-are formedradiallyaroundthe forward and rearward ends; of the .outerrotary element I57, inline with the blades I56v and buckets I60.

The trailing side of the outer rotary element I51 is provided with acylindrical extension I54 on-Which is. formed a ring gear H56. Planetarygears I63 are mounted on shafts no supported in bearing support I12. Thebearing support I72 is constructed similarly to the bearing support 24.of Figurel. on-the shaft I54, meshes with the planetary gears I68.

The combustion driving; means of Figure 4 is indicated generally at I16.and is supported on thetrailing end of the shaft I54 to rotate freelythereon.

Formed in the leading side of the driving means H6 is a ring gear I18,with which mesh planetary gears I80 on the rear ends of the shaft III Asun gear. I82 is fixedly secured on the shaft I54 imposition to meshwith the planetary gears I 80.

The remaining features of the device of Figure; are the same or similarto corresponding features of the device of Figure l and in part areillustrateddiagrammatically in Figure 3.

Operation of the device in Figure 4 Upon rotation of the driving meansIII; the outer rotary element I5! of the, compressor rotates in thesamedirection as the driving means. Since both areconnected tocorresponding parts of; similar planetary gearing, the central rotaryelement I52,of thecompressor rotates in a direction opposite to that ofthe driving means and therefore in the opposite direction of the outerrotary element I58;

.Theeffect of such; counter-rotation therefore The device of Figure 5The device shown in Figure 5 is similar to that of Figure 1, but thegearing between the combustion driving means and the shaft iseliminated, In such a construction, fuel may proceed directly fromthepassage I 24, into thehole low drum I86, andthrough the passages I8and 80., nd, Jets, 82...

A sun gear I'M, fixedly secured In hepr entinstance Fi ura he c m us.

' tral rotary element 48 thereof is fixedly secured to the shaft I88. Insuch a devicethe rotary element of the compressor and the driving meansrotate in the same direction. Efiiciency is gained by the elimination ofthe gearing between the driving means and the shaft. However, it may bedesirable to provide a gearing just mentioned, instead of eliminatingit, to cause greater rotation of the compressor element than of thedriving element. If it should happen that the speed of the drivingelement would be limited due to the presence of intensive heat, or othercauses, it should not be necessary to limit the speed of the rotaryelement of the compressor, for the same reasons. The rotary element ofthe compressor is relatively cold and may attain greater speed-andcentrifugal force for building up greater pressures.

The efiiciency of the device is improved due to the fact that combustiontakes place directly in the rotary driving means. guished from previoustypes of jet motors where gases passed from a stationary combustionspace to a turbine driving element with consequent loss of efilciency.In the present device such loss of efiiciency, is eliminated.

While I have herein shown preferred embodiments of my invention, it willbe understood of course that I do not wish to be limited thereto sincemany modifications may be made, and I therefore contemplate by theclaims appended hereto to cover any such modifications or substitutionsof equivalents as fall within the true spirit and scope of my invention.

I claim:

'1. In a jet motor, a casinghaving open ends, a rotatable combustiondriving means in said casing having a plurality of radial blades, eachpair of adjacent radial blades bounding a combustion chambertherebetween, a fuel passage adapted for connection with a source offuel, said fuel passage extending through said combustion driving means,and a plurality of passages leading from said fuel passage and extendingthrough said blades and terminating in jets opening into the combustionchambers between the blades.

2. In a jet motor, a casing having open ends, a rotatable combustiondriving means in said casing having a plurality of radial blades, eachpair of adjacent radialblades bounding a combustion chambertherebetween, a fuel passage adapted for connection with a source offuel, said fuel passage extending through said combustion driving means,and a plurality of passages leading from said fuel passage and extendingthrough said blades and terminating in jets, said jets being positionedat the outer tips of said blades and opening into the combustionchambers between the blades in a direction opposite to the direction ofrotation of said combustion driving means.

3. In a jet motor, a casing having open ends, a rotatable combustiondriving means in said casing having a plurality of radial blades, eachpair of adjacent radial blades'bounding a combustion chambertherebetween, said blades being disposed at an angle with respect to theaxis of the combustion driving element, about their respective radialaxes, a fuel passage adapted for This is distin onnection with a sourceof fuel, said fuel passage extending through said combustion drivingmeans, a plurality of passages leading from said fuel passageandextending through said blades andterminating in jets opening into the arotatable combustion driving means in said casing having a plurality ofradial blades, said radial blades forming combustion chamberstherebetween, said combustion chambers being of reduced dimension towardthe leading end of said casing, and means including, passages throughsaid blades terminating tangentially thereof for injecting fuel intosaid combustion chambers.

5. In a jet motor, a casing having open ends, a shaft rotatable in saidcasing, a bearing support in said casing, said bearing support havingradial fins secured to said casing, and combustion driving means mountedon said shaft downstream of said bearing support, and a fuel passageadapted for connection with a source of fuel, said fuel passageextending through one of said fins in said bearing support, through saidshaft, and through said combustion driving means and having an outlettherein.

6. In a jet motor, a casing having open ends, a shaft rotatable in saidcasing, a bearing support in said casing, said bearing support havingradial fins secured to said casing, and a combustion driving meansmounted on said shaft, said combustion driving means having blades atits outer portion, thereby forming an annular air passage through saidcasing, and a fuel passage adapted for connection with a source of fuel,said fuel passage extending through one of said fins in said bearingsupport, through said shaft, and through the blades of said combustiondriving means and having tangential outlets therein, said fuel passagehaving a second outlet opening out of said fin of said bearing supportinto said annular air passage and into said combustion driving means,and ignition means in said annular air passage adjacent said secondoutlet.

7. In a jet motor having a rotatable shaft and combustion driving meansrotatable on said shaft, said driving means comprising, in combination,a hub adapted for mounting on said shaft, a plurality of bladesextending radially from said hub, there being passages in said bladesleading from said hub outwardly and terminating in jets opening out ofsaid blades tangentially thereof, said blades being disposed at anangle, with respect to the axis of said hub, about their respectiveradial axes, said blades being restricted between their edges so thatthe spaces between adjacent blades have restricted dimensions atopposite ends in a direction axially of said driving means, and meansfor supplying fuel through said passages.

8. In a jet motor, a casing having open ends adapted for flow of airtherethrough, a shaft in said casing, an axial flow rotor on said shaft,a plurality of radial blades on said rotor, each blade having a leadingedge and a trailing edge, the leading edge being offset from thetrailing edge in the direction of rotation of said rotor, each bladehaving a leading face and a trailing face, the leading face of eachblade and the opposite facing trailing face of the previous blade beingshaped to form therebetween a flow passageway having an enlargedcombustion chamber formed intermediate the ends thereof, and fuelpassages in said blades opening to the combustion chambers.

9. A jet motor as set forth in claim 8, wherein said fuel passagesextend radially through said blades and terminate in jets positionedadjacen the outer tips of the blades.

10. A jet motor as set forth in claim 8, wherein the fuel passages opento the combustion chamber through the trailing face of the blade.

11. A jet motor as set forth in claim 8, wherein the fuel passages openin a diretcion opposite to the direction of rotation of the rotor.

12. A jet motor as set forth in claim 8, wherein the fuel passages openthrough the trailing face of the blade in a direction having a componenttangent to the trailing face of the blade.

13. A jet motor asset forth in claim 8,, wherein said faces of theblades form a throat in said flow passageway downstream of saidcombustion chamber and also form an expansion nozzle downstream of saidthroat.

14. In a jet motor, a casing having open ends adapted for flow of airtherethrough, a shaft in .said casing, an axial flow rotor on saidshaft. a

plurality of radial blades on said rotor,each blade having a leadingedge and a trailing edge, the leading edge being offset from thetrailing edge in the direction of rotation of said rotor, each bladehaving a leading face and a trailing face, the leading face of eachblade and the opposite facing trailing face of the previous blade beingshaped to form therebetween a flow passageway having an enlargedcombustion chamber formed intermediate the ends thereof, a plurality ofaxially spaced sets of fins upstream of the rotor, the last set of finsthrough which the air passes before it enters said rotor being disposedat an angle to the axis of the motor, and the axes of said combustionchambers being straight and extending parallel to said last set of fins.

15. In a jet motor, a casing having open ends adapted for flow of airtherethrough, a. shaft in said casing, an axial flow rotor on saidshaft, and a plurality of radial blades on said rotor, each blade havinga leading edge and a trailing edge, the leading edge being offset fromthe trailing edge in the direction of rotation of said rotor, each bladehaving a leading face and a trailing face, the leading face of eachblade and the opposite facing trailing face of the previous blade beingshaped to form therebetween an axial flow passageway comprising, inorder passing downstream, a first throat, a combustion chamber ofenlarged width, a second throat, and an expansion nozzle.

16. In a jet motor, a casing having open ends adapted for flow of airtherethrough, a shaft in said casing, an axial flow rotor on said shaft.a plurality of radial blades on said rotor, each blade having a leadingedge and a trailing edge, the leading edge being offset from thetrailing edge in the direction of rotation of said rotor, each bladehaving a leading face and a trailing face, the leading face of eachblade and the opposite facing trailing face of the previous blade beingshaped to form therebetween a flow passageway having an enlargedcombustion chamber formed intermediate the ends thereof, the axes ofsaid combustion chambers being straight and disposed at an angle to theaxis of the motor, a throat in each said flow passageway downstream ofsaid combustion chamber and an expansion nozzle downstream of saidthroat, and the portion of the blade leading face downstream of theexpansion nozzle extending axially of the com-- bustionchainberakisfurther than the portion of the blade trailing face downstream of theexpansion nozzle, whereby the flow issuing from the fiow passageway isturned toward a direction parallel to said motor axis. V

17, In a jet motor, a casing having open ends,

ashaft in said casing, radial fins between said shaft and said casing, acombustion driving means on said shaft downstream of said radial fins, afuel passage adapted for connection with a sourceof fuel, said fuelpassage extending through one of said fins, through said shaft, and

through said combustion driving means and havingan outlet therein, saidfuel passage having a second outlet opening in said fin, said secondopening facing in a direction downstream of the and ignition meansbetween said fin and said combustion drive means adjacent said secondThe following references are of record in the file of this patent:

Number Number I2 UNITED STATES PATENTS Name -Date Gordon May 29,1934Lysh01m :May 18,1937 Graves Jan. 28,1941 Jendrassik 'May 27,1941 ZiglerJuly 22,1941 Seippel Aug.3, 1943 Birg'e June 26, 1945 Biichi -Dec.11,1945 Walton Nov. 5,1946 Vernon Aug. 19, 1947 Emigh 'Mar. .29, 1949Price Aug. 23, 1949 FOREIGN PATENTS Country Date Great Britain- Oct. 18,1906 Great-Britain Dec. 18, 1930

